Aeroplane.



L. R. RODNEY.

ABROPLANE.

APPLICATION FILED JULY 22, 1911.

Patented June 11, 1912.

' 3 BHEET8SHEET 1.

8mm LwwreneeRflomua L. R. RODNEY.

AEROPLANE. APPLICATION FILED JULY 22, 1911.

Patented June 11, 1912.

3 SHEETS-SHEET 2.

3mm Lawrence Rjzooney.

L. R. RODNEY.

AEROPLANE.

APPLICATION nun JULY 22, 1911. 1,028,968. Patented June 11, 1912.

" a agnnws snm a. x L 2 l4 I- ISL-Z:- 4 1 I I Lawren ae ERDOTI 83 LAWRENCE ROBERT ROONEY, OF HOLLIDAYSIBURG, PENNSYLVANIA.

AEROPLANE.

Specification of Letters Patent.

Patented June 11 1912.

Application filed July 22, 1911. Serial No. 639,922:

To, all whom it may concern:

Be it known that I, LAWRENCE R.ROONEY, a citizen of the United States, residing at Hollida'ysburg, in the county of Blair and State of Pennsylvania, have invented certain new anduseful Improvements in Aeroplanes, of which the following is a specification, reference being had to the accompanying drawings;

.My invention relates to new and useful improvements in aeroplanes and more particularly to a monoplane, and my object is to providea machine of this character provided with a pair of balancing wingtips or ailerons and ready means for the operation of the same by the aeronaut.

A further object of the invention resides in providing a tail plane comprising a ver tical rudder movable on a vertical axis of the machine to guide the same laterally and a pair of elevating rudders operable on horizontal axes on said vertical rudder, and a further object resides in the provision of means for the operation of said rudders;

A still further object of the invention resides in providing means whereby the operation-of the vertical rudder and the wing tips or ailerons may be simultaneously accomplished.

A still further object resides in providing a lever formed in sections, the sections of. {which are operable onaxes. at right angles to one another, and the one section forming a handle or the like for the other section.

A still further object resides in providing a machine which is extremely simple in construction, whereby the same will be com- 7 a part of this application, Figure 1 1s a perspective view of the device: Fig. 2 is a bottom plan view thereof. Fig. 3 is an enlarged detail perspective view of the sectional operating lever in position on the device. Fig. 4 is a similar view of one of the balancing wing tips or ailerons. Fig; 5 is a detail perspective view of the vertical and horizontal rudders, and Fig. 6 is a similar view of one of the horizontal rudders removed.

In carrying out my invention, I shall refer to the drawings in which similar'refer- ,ence characters designate corresponding parts throughout the several views and in which lindicates an elongauid frame consisting of an upper and lower pair of bars 2 and 3, respectively, said bars being held in spaced alinement withone another by means of the vertical and horizontal bracing bars 4, and the upper and lower bars 2 and 3 are inclined so as to converge at their rear ends. Mounted on the forward end of the frame 1 to extend transversely thereof, is a main supporting plane 5, said plane being provided with an opening about. centrally the width of the frame 1, the purpose of which will be hereinafter and more particularly described, and extending from the lower bars 3 of the fran'ie downwardly at an angle toward the forward end of the same, isa pair of bars 6, said bars having secured thereto, a transversely extendin arm 7, theends 'of this latter arm being bifurcated and secured to the outer frame-work of the plane on opposite sides of the frame, thereby securely bracing said plane. The bars 6 converge at the ends thereof-opposite those secured to-the bars 3 and indirectly support a pair of arms 8, the lower ends of which are secured to the front-axle 9. This axle has rotatably mounted on the ends thereof,

the forward wheels 10, whereby the forwardend of the machine may be supported on the ground. Secured to the lower bar 3 of said frame adjacent the rear end thereof, is a pair of dependentand convergent arms -11. The lower ends of said arms indirectly support an additional pair of arms or brackets 12 carrying a rear axle 13. Upon the outer ends of the rear axle, are mounted the rear wheels 14, whereby the rear end of the frame is supported on the ground, as is usual in numerous machines of this type.

15, and the rear end of said bar has rotatably mounted therein,- the lower end of a vertical shaft 17. the upper end of said shaft being similarly mounted in the extreme rear transverse bracing bar 4. Carried on the vertical shaft 17, is a vertical rudder 18, that is. the rudder which guides the machine laterally. and carried on this vertical rudder, is a pair of elevating rudders 19. These latter rudders are disposed longitudinally of the frame, the'same being slotted, as shown at 20, to receive therein, the rudder l8, and the forward ends of said rudders 19 are pivotally connected on the frame of the rudder 1S and movable on horizontal axes at right angles to the axis of the vertical rudder.

Supported bet-ween the pair of inclined bars (3 and braced to the frame 1, is a seat 21, upon one side of which is pivotally mounted intermediate of its length, a lever 22, the upper and lower ends of lever having, respectively, connected thereto, the ends of wires or other flexible connections 23 and 2t. One of these wires is extended to one side of the frame 1, while the other is extended to the opposite side of the frame,

said wiresbeing guided to the rear of the frame where they have their opposite ends connected, respectively, to the ends of a transverse bar 25 carried on thevertical shaft 17 of the vertical rudder. From this construction, it will be seen that as said lever is thrown in one direction, one of the wires will be drawn tocorrespondingly draw said rudder in one direction, while when the lever is moved in an opposite d1-- rection, said rudder will be likewise moved or aileron in the opposite direction, and thus,- the machine may be guided laterally by the aeronaut in the seat. livotally mounted on the opposite side of the seat 21 and intermediate of its length, is an additional lever 26, one end of which has secured thereto, a wire 27 which leads rearwardly of the frame 1 and is guided on the rudder 18 and is secured to one of the vertical rudders 19. An additional wire 28 secured to said lever on the opposite side of the pivotal point thereof, is guided rearwardly of the frame and secured to the other of said rudders 19, and thus, it will be seen that as said lever is moved in one direction, the rudders 19 will be inclined upwardly, and when said lever is mo (ed in the opposite direction, said pair of rudders will be disposed or inclined downwardly to correspondingly cause the ascentor descent of the machine, as desired.

Pivotally secured on each end of the inner side edges of the plane 5, is a wing tip each of said ailerons bein )rovided with a bar 30 extendin res ectively, above and below the upper and lower faces of the same. A wire 31 guided along the rear edge of the plane to points thereon contiguous with the wing tips or ailerons 29 and has the ends there of, resptectively, engaged with the lower ends of the bars 30 thereof, and the two wires 32 and 33 which are also guide-d along the rear edge of said frame 1., have the outer ends thereof secured to the upper ends of the bars 30, while the inner ends of said wires are engaged with a section 34 of the additional lever 26. This section 24 forms a pivotal handle on the lever 26, the same being pivotally mounted thereon on an axis at right angles to the pivotal axis of the lever 26 proper, and thus, it will be seen that as the lever 26 is operated forwardly and rearwardly by the aeronaut in the seat, the section 3t may be simultaneously operated to operate the wing tips or ailerons at the ends of the plane It will be noted, however, in view of the particular connecttion of the wires to said ailerons that as one of the latter is raised, the other lowered, and vice versa.

Mounted on the frame 1 in the forward end thereof within the open space formed in the plane 5, is a niotor of any preferred type, said motor having operable connection with a shaft 36 rotatably carried on said frame 1; The forward end of the shaft 36 protrudes or extends beyond the forward end of the frame 1 and carries thereon, an enlarged propeller 37-. tl'irough-the means of which the machine is driven. Any desired means may be provided whereby the engine may be readily operated by the aeronaut in the seat, but as this means does not form any essential part of my invention, I

do not deem it necessary to describe the the aeronaut to rise as the machine is driven forwardly, the lever 26 is moved in a direc tion so as to dispose the pair of elevating rudders 19 atan angle downwardly, and upon reaching the desired height, said lever is moved to a position to throw said elevating rudders 19 irfa substantially horizontal position. Should the aeronaut desire to make a turn at any time while in the air, the lever 22 may be operated to throw the rudder 18 in either one direction or the other to correspondingly turn the machine in the opposite direction, and as both the lever 22 and the lever 26 are at close range to the aeronaut, the machine may be under perfect cont-r01 at all times. In making the various turns in the air and particularly in making an ascent or descent, it may happen that the machine becomes overbalanced on one side or the other, and in order to obviate this dif- 5, extends l ficulty, or rather compensate for such overwardly and downwardly. As the operation "-of these wing tips or ailerons will not require the aeronaut to releasehis hold upon the levers, it will be seen that there will be little or no possibility of the machine losing its longitudinal stability, and thus many accidents, which are so prevalent at the presout time, will be avoided. a

At any time should the aeronaut desire t descend, the lever 26 is operated so as to dispose the elevating and descending rud .ders 19 at an angle upwardly, whereby such descending may be readily accomplished with little or no difliculty.

From the foregoing, it will be seen that I have provided a flying machine of the monoplane type which is practically operative and which is of such, simple construction and has so few operating parts as to be under perfect control at all times. It will still further be seen that I have provided a tail plane comprising a vertical rudder and a pair'of elevating and descending rudders, the latter rudders being operable on axes at right angles to the axis of the first referred to rudder. Furthermore, it will be seen that I have provided balancing wing tips or ailerons carried on the ends of the main supporting plane, which ailerons may be operated simultaneously with the operation of the elevating and descending rudders. It will still further be seen that I have provided a lever formed in sections, one section ofv which has connection with the elevating rudders, while the other \section forms a handle for the first referred to section and has connection with the wing tips or ailerons for the operation thereof. It will still further be seen that the sections of ,c this lever are pivoted on axes at right angles to one another.

.It will still further be seen that this machine is of such simple construction as to be comparatively cheaply manufactured and one which is and one which may be effectively and. safely operated in ried thereon, a vertical rudder in the rear of said frame, means for the operation of the same, additional horizontal rudders carried on said mentioned rudder, ailerons pivotally carried on the ends of said supporting plane, alever carried on said frame and formed in sections, one of said sections being operatively connected to the last mentioned rudders, the other section being similarly connected to said ailerons, and both of said sections being pivotally operable on axesat right angles to one another.

2. In an aeroplane, the combination with a frame, a main supporting plane carried thereon, a verticalrudder carried on the rear of said frame, means for the operation of the same, additional horizontal rudders carried on said mentioned rudder, ailerons carried on the ends of said supporting plane, a lever pivotally mounted on said frame and having operative connection with the last mentioned rudders, and a pivotal handle for c said lever operable on an axis at right angles to the axis of the lever proper, said handle member having operative connection with said ailerons, whereby the same may be simultaneously operated with the operation of the last mentioned rudders.

3. In an aeroplane, a frame, a main supporting plane carri'ed thereon, ailerons carried on the ends of said supporting plane, a rudder mounted on a vertical axis at the rear end of said frame, a lever fulcrumed on the frame andoperatively connected to said vertical rudder, additional rudders pivoted on a horizontal axis to the frame of the last mentioned rudder and slotted to receive therethrough said last mentioned rudder, an additional lever fulcrumed on the side of the frame opposite that carrying the aforesaid lever, said latter lever having operative connection with said horizontal rudders, a handle member pivoted to the last mentioned lever on an axis disposed at right angles to the axis of the latter, and means connecting said pivoted handle member to said ailerons, whereby the latter may be op erated simultaneously with the operation of said horizontal rudders.

Initestimony whereof I hereunto afiix my signature in the presence of two witnesses.

LAWRENCE ROBERT ROONEY. Witnesses:

W; H. HARPSTED, JOHN E. SHELLENBERGER'. 

